[Federal Register Volume 68, Number 90 (Friday, May 9, 2003)]
[Rules and Regulations]
[Pages 24861-24864]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-11265]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-44-AD; Amendment 39-13142; AD 2003-09-13]
RIN 2120-AA64
Airworthiness Directives; the New Piper Aircraft, Inc. Models PA-
23, PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-23,
PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 airplanes that do not
incorporate a certain design flap control torque tube or torque tube
assembly. This AD requires you to repetitively inspect the flap control
torque tube for cracks, corrosion, wear, or elongation of the
attachment bolt holes (referred to as damage); and requires you to
replace any damaged torque tube with either an improved design flap
control torque tube or flap control torque tube assembly. The
repetitive inspections will no longer be necessary when the improved
design torque tube or torque tube assembly is installed. This AD is the
result of several reports of damage found in the flap control torque
tube on the affected airplanes. The actions specified by this AD are
intended to detect and correct damage to the flap control torque tube,
which could result in failure of the flap operating system. If such
failure occurred during landing or takeoff, then a split flap condition
[[Page 24862]]
could occur with potential loss of control of the airplane.
DATES: This AD becomes effective on June 23, 2003.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulations as of June
23, 2003.
ADDRESSES: You may get the service information referenced in this AD
from The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive,
Vero Beach, Florida 32960; telephone: (561) 567-4361; facsimile: (772)
978-6573. You may view this information at the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2002-CE-44-AD, 901 Locust, Room 506, Kansas
City, Missouri 64106; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Hassan Amini, Aerospace Engineer, FAA,
Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix
Boulevard, Suite 450, Atlanta, Georgia 30349; telephone: (770) 703-
6080; facsimile: (770) 703-6097.
SUPPLEMENTARY INFORMATION:
Discussion
What Events Have Caused This AD?
A review of FAA's service difficulty report (SDR) database shows
several incidents of cracks and corrosion in the flap control torque
tube on Piper PA-23 series airplanes. One incident of a broken flap
control torque tube resulted in a split flap condition during approach.
What Is the Potential Impact if FAA Took No Action?
Cracked or corroded flap torque tubes, if not detected and
corrected, could result in damage to the flap control torque tube and
failure of the flap operating system. If such failure occurred during
landing or takeoff, then a split flap condition could occur with
potential loss of control of the airplane.
Has FAA Taken Any Action to This Point?
We issued a proposal to amend part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include an AD that would apply to
certain Piper Models PA-23, PA-23-160, PA-23-235, PA-23-250, and PA-
E23-250 airplanes that do not incorporate a certain design flap control
torque tube or torque tube assembly. This proposal was published in the
Federal Register as a notice of proposed rulemaking (NPRM) on January
27, 2003. The NPRM proposed to require you to repetitively inspect the
flap control torque tube for cracks, corrosion, wear, or elongation of
the attachment bolt holes; and would require you to replace any damaged
flap control torque tube with either an improved design flap control
torque tube or flap control torque tube assembly. The repetitive
inspections would no longer be necessary when the improved design flap
control torque tube or flap control torque tube assembly is installed.
Was the Public Invited To Comment?
The FAA encouraged interested persons to participate in the making
of this amendment. We did not receive any comments on the proposed rule
or on our determination of the cost to the public.
FAA's Determination
What Is FAA's Final Determination on This Issue?
After careful review of all available information related to the
subject presented above, we have determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. We have determined that these minor
corrections:
--Provide the intent that was proposed in the NPRM for correcting the
unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
How Does the Revision to 14 CFR Part 39 Affect This AD?
On July 10, 2002, FAA published a new version of 14 CFR part 39 (67
FR 47997, July 22, 2002), which governs FAA's AD system. This
regulation now includes material that relates to special flight
permits, alternative methods of compliance, and altered products. This
material previously was included in each individual AD. Since this
material is included in 14 CFR part 39, we will not include it in
future AD actions.
Cost Impact
How Many Airplanes Does This AD Impact?
We estimate that this AD affects 3,733 airplanes in the U.S.
registry.
What Is the Cost Impact of This AD on Owners/Operators of the Affected
Airplanes?
We estimate the following costs to accomplish the inspection:
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Total cost on U.S.
Labor cost Parts cost Total cost per airplane operators
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8 workhours x $60 per hour = $480.... None for inspection.... $480 per airplane...... $1,791,840.
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We estimate the following costs to accomplish any necessary
replacement that will be required based on the results of the
inspection. We have no way of determing the number of airplanes that
may need such repair/replacement:
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Total cost per
Labor cost Parts cost airplane
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4 workhours x $60 per hour = $452 per airplane. $692 per airplane.
$240.
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Regulatory Impact
Does This AD Impact Various Entities?
The regulations adopted herein will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
Does This AD Involve a Significant Rule or Regulatory Action?
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a
[[Page 24863]]
``significant rule'' under DOT Regulatory Policies and Procedures (44
FR 11034, February 26, 1979); and (3) will not have a significant
economic impact, positive or negative, on a substantial number of small
entities under the criteria of the Regulatory Flexibility Act. A copy
of the final evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2003-09-13 The New Piper Aircraft, Inc.: Amendment 39-13142; Docket
No. 2002-CE-44-AD.
(a) What airplanes are affected by this AD? This AD affects the
following airplane models and serial numbers that are certificated
in any category and do not incorporate a part number (P/N) 17634-002
flap control torque tube; or a P/N 104622-002 or 104622-004 flap
control torque tube assembly:
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Model Serial numbers
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PA-23 and PA-23-160 23-1 through 23-2046.
PA-23-235 27-505 through 27-622.
PA-23-250 27-1 through 27-504 and 27-2000
through 27-8154030.
PA-E23-250 27-2505 through 27-4916 and 27-
7304917 through 27-7554168.
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(b) Who must comply with this AD? Anyone who wishes to operate
any of the airplanes identified in paragraph (a) of this AD must
comply with this AD.
(c) What problem does this AD address? The actions specified by
this AD are intended to detect and correct damage to the flap
control torque tube, which could result in failure of the flap
operating system. If such failure occurred during landing or
takeoff, then a split flap condition could occur with potential loss
of control of the airplane.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Inspect the flap control Initially inspect In accordance with
torque tube for cracks, upon accumulating sections 3 through
corrosion, wear, or 2,500 hours time-in- 10 of the
elongation of the service (TIS) on ACCOMPLISHMENT
attachment bolt holes the flap control INSTRUCTIONS
(referred to as damage). torque tube or section of Piper
within the next 100 Mandatory Service
hours TIS after Bulletin No. 1051B,
June 23, 2003 (the dated November 5,
effective date of 2002.
this AD), whichever
occurs later.
Repetitively
inspect thereafter
at intervals not to
exceed 500 hours
TIS until a
replacement flap
control torque tube
or flap control
torque tube
assembly specified
in paragraph (d)(2)
of this AD is
installed.
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(2) Replace any damaged flap Prior to further In accordance with
control torque tube and flight after the sections 3 through
replace any wooden end inspection where 10 of the
plugs with new plastic end damage is found. ACCOMPLISHMENT
plugs, P/N 17631-002. INSTRUCTIONS
Replace the flap control section of Piper
torque tubes with either a Mandatory Service
P/N 17634-002 flap control Bulletin No. 1051B,
torque tube or a P/N 104622- dated November 5,
002 or 104622-004 flap 2002.
control torque tube
assembly.
(i) The P/N 17631-002 end
plugs are part of the P/N
104622-002 and 104622-004
flap control torque tube
assemblies, but must be
obtained for the P/N 17634-
002 installation.
(ii) You do not have to
inspect the existing wooden
end plugs as specified in
the service bulletin since
this AD requires the
installation of plastic end
plugs.
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(3) The repetitive You may replace the In accordance with
inspections required by flap control torque sections 3 through
this AD may be terminated tube assembly at 10 of the
after installation of a any time, but must ACCOMPLISHMENT
replacement flap control replace prior to INSTRUCTIONS
torque tube or flap control further flight if section of Piper
torque tube assembly as damage is found Mandatory Service
specified in paragraph during an Bulletin No. 1051B,
(d)(2) of this AD. inspection. dated November 5,
2002.
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(e) Can I comply with this AD in any other way? To use an
alternative method of compliance or adjust the compliance time, use
the procedures in 14 CFR 39.19. Send these requests to the Manager,
Atlanta Aircraft Certification Office. For information on any
already approved alternative methods of compliance, contact Hassan
Amini, Aerospace Engineer, FAA, Atlanta Aircraft Certification
Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450,
Atlanta,
[[Page 24864]]
Georgia 30349; telephone: (770) 703-6080; facsimile: (770) 703-6097.
(f) Are any service bulletins incorporated into this AD by
reference? Actions required by this AD must be done in accordance
with Piper Mandatory Service Bulletin No. 1051B, dated November 5,
2002. The Director of the Federal Register approved this
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51.
You may get copies from The New Piper Aircraft, Inc., Customer
Services, 2926 Piper Drive, Vero Beach, Florida 32960; telephone:
(561) 567-4361; facsimile: (772) 978-6573. You may view copies at
the FAA, Central Region, Office of the Regional Counsel, 901 Locust,
Room 506, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) When does this amendment become effective? This amendment
becomes effective on June 23, 2003.
Issued in Kansas City, Missouri, on April 30, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-11265 Filed 5-8-03; 8:45 am]
BILLING CODE 4910-13-U